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EP2500520A2 - Dämpfer- und Dichtungsanordnung für eine Turbinenschaufel - Google Patents

Dämpfer- und Dichtungsanordnung für eine Turbinenschaufel Download PDF

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Publication number
EP2500520A2
EP2500520A2 EP12158501A EP12158501A EP2500520A2 EP 2500520 A2 EP2500520 A2 EP 2500520A2 EP 12158501 A EP12158501 A EP 12158501A EP 12158501 A EP12158501 A EP 12158501A EP 2500520 A2 EP2500520 A2 EP 2500520A2
Authority
EP
European Patent Office
Prior art keywords
bucket
shank portion
pin
oriented groove
groove
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12158501A
Other languages
English (en)
French (fr)
Other versions
EP2500520A3 (de
EP2500520B1 (de
Inventor
Bradley Boyer
Matthew D. Collier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2500520A2 publication Critical patent/EP2500520A2/de
Publication of EP2500520A3 publication Critical patent/EP2500520A3/de
Application granted granted Critical
Publication of EP2500520B1 publication Critical patent/EP2500520B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates generally to turbomachines and particularly, to damper pins and seal pins disposed between adjacent buckets on a rotor wheel.
  • turbines generally include a rotor comprised of a plurality of rotor wheels, each of which mounts a plurality of circumferentially-arranged buckets.
  • the buckets each typically include an airfoil, a platform, a shank and a dovetail, the dovetail being received in mating dovetail slot in the turbine wheel.
  • the airfoils project into a hot gas path downstream of the turbine combustors and convert kinetic energy into rotational, mechanical energy.
  • vibrations are introduced into the turbine buckets and if not dissipated, can cause premature failure of the buckets.
  • Vibration dampers are often in the form of elongated damper pins that fit between adjacent buckets and provide the damping function by absorbing harmonic stimuli energy produced as a result of changing aerodynamic loading.
  • a damper pin is typically retained in a groove formed along one circumferentially-oriented "slash face" in the turbine blade shank region of one of each pair of adjacent buckets. The damping pin is centrifugally loaded during operation and, in order to prevent bucket-to-bucket binding, the groove must be machined so as to allow the pin to float relatively freely within the groove.
  • the cooling efficiency can also be impaired by ingress of hot gas from the hot gas path into the bucket shank region.
  • the damper pin has reduced-cross-section ends supported on shoulders formed in the bucket shank, with or without annular seals at the interfaces between the reduced-cross-section ends and the main body portion of the pin to minimize leakage along the damper pin groove.
  • a further approach to seal against cross-shank leakage is to provide radial seal pins between the shanks of adjacent buckets at the fore and aft ends of the shank, below the axially-extending damper pin.
  • the radial seal pins are seated in seal pin grooves formed on the same slash face as the damper pin groove, and engage the substantially flat sides of the shank of the adjacent bucket. The sealing effectiveness of these cross-shank seals is an important factor in increasing the bucket life by minimizing thermal stress.
  • the invention relates to a bucket pair in a turbomachine comprising: a first bucket having a first airfoil portion and a first shank portion; a second adjacent bucket having a second airfoil portion and a second shank portion adjacent the first shank portion; a substantially axially-oriented groove in the first shank portion; at least one substantially radially-oriented groove in the second shank portion; an elongated damper pin seated in the substantially axially-oriented groove in the first shank portion; and an elongated radial seal pin seated in the at least one substantially radially-oriented groove in the second shank portion.
  • the invention in another exemplary but nonlimiting aspect, relates to a bucket for a turbomachine rotor wheel comprising an airfoil portion, a shank portion and a dovetail mounting portion, the shank portion including opposite sides, one of said sides formed with a substantially axially-oriented groove extending between forward and aft ends of the shank portion, and the other of the sides formed with a least one substantially radially-oriented groove, the substantially axially-oriented groove adapted to receive an elongated damper pin, and the at least one substantially radially-oriented groove adapted to receive an elongated radial seal pin.
  • the invention in still another exemplary but nonlimiting aspect, relates to bucket and pin assembly for a turbine machine rotor wheel comprising a bucket formed with an airfoil portion, a shank portion and a dovetail mounting portion, the shank portion including opposite sides each adapted to face respective adjacent buckets when installed on a rotor wheel, one of the opposite sides of the shank portion formed with a substantially axially-oriented groove extending between forward and aft ends of the shank portion, and the other of the opposite sides formed with at least one substantially radially-oriented groove at a forward end of the bucket; an elongated damper pin seated in the substantially axially-oriented groove, and a radial seal pin located in the at least one substantially radially-oriented groove.
  • Fig. 1 illustrates a conventional turbine blade or bucket 10 including an airfoil 12, a platform 14, a shank 16 and a dovetail 18.
  • the dovetail 18 is utilized to secure the bucket 10 to the periphery of the rotor wheel (not shown), as is well understood in the art.
  • a damper pin 20 is located along one axial edge (or slash face) 22 adjacent (i.e., radially inward of) the bucket platform 14 with the leading end 24 of the damper pin 20 located nearer the leading edge of the bucket, and the trailing end 26 of the damper pin located nearer the trailing edge of the bucket.
  • a similar pin 20 is located between each adjacent pair of buckets 18, 118 on the turbine wheel, as apparent from Fig. 2 .
  • the damper pin 20 is located in a groove 28 ( Fig. 1 ) extending along the entire slash face 22 of the bucket 118.
  • the damper pin 20 may include a substantially cylindrical body portion 30 between a pair of substantially semi-cylindrical, opposite ends 24, 26 interfacing at shoulders 39. This configuration creates flat support surfaces 32, 34 (best seen in Fig. 1 ) that are adapted to rest on the machined bucket platform surfaces or shoulders (not shown in Fig. 1 but one shown at 36 in Fig. 2 ) at opposite ends of the groove 28 formed in the bucket slash face, thereby providing good support for the pin while preventing undesirable excessive rotation during machine operation.
  • Fig. 3 illustrates a bucket 37 with a long bucket shank where radially-oriented seal pins 38, 40 are used in combination with a damper pin 42. Note, however, that there is still a considerable gap between the radially outer ends 52, 54 of the seal pins 38, 40 and the ends 48, 50 of the damper pin 42. Note also that the groove or slot 18 in which the damper pin is located is open at both ends, allowing cooling air to escape through the clearance spaces between the pin and the groove in which it is seated, especially along the reduced-cross-section ends 48, 50.
  • each bucket in a circumferential row of buckets is formed such that the damper pin/seal pins seated in grooves formed on one side of a bucket engage flat surfaces of an opposite side of an adjacent bucket.
  • a modified bucket 56 (having an airfoil portion 12 and dovetail mounting portion 18) includes opposite sides 58, 60 of the shank portion 62.
  • Side 58 is formed to include a substantially axially-oriented damper pin groove 64 that is substantially similar to the damper pin groove 28, with flat support surfaces 66, 68 at opposite ends, adapted to receive the damper pin 20, with reduced cross-section ends 24, 26 adapted to seat on the support surfaces 66, 68.
  • a flat surface 112 radially inward of the axially-oriented groove there is a flat surface 112 radially inward of the axially-oriented groove.
  • the opposite side 60 of the shank portion 62 is formed with radial seal pin grooves 70, 72, that are adapted to receive radial seal pins similar to those shown at 38, 40.
  • Fig. 6 shows a prior configuration for a bucket pair where a damper pin 74 having a round cross-sectional shape with reduced cross-sectional ends (one shown at 76)is relatively loose seated in a substantially axially-oriented groove 80 formed in the shank portion 82 of a first bucket 84 (similar to groove 64 in Fig. 4 ).
  • the groove 80 is formed with a support surface 86 for the pin end 78 (similar to surface 68 in Fig.4 ).
  • An elongated radial seal pin 88 (of substantially uniformly round cross-sectional shape) is also relatively loosely seated in a substantially radially-oriented groove 90 that is formed on the same side of the shank portion 82 of the first bucket 84.
  • the damper pin 74 in use, is engaged with an undercut or wedge surface 79 on the shank portion 82 of the first bucket and an undercut or wedge surface 92 on the shank portion 94 of the second adjacent bucket 96.
  • the radial seal pin 84 in groove 90 is engaged with a flat surface 98 on the shank portion 94 of the adjacent bucket 96.
  • the cooling fluid leakage path is shown at 100.
  • the damper pin 74, groove 80, reduced end 78 and support surface 86 are provided in the shank 102 of the first bucket 104, similar to the damper pin arrangement in Fig. 6 .
  • a substantially radially-oriented radial groove 106 is formed in the shank portion 108 of the adjacent second bucket 110.
  • Damper pin 74 projects beyond the groove 80 and remains engaged with the wedge surfaces 112, 114, respectively on the adjacent bucket shank portions, and the radial seal pin 88 in groove 106 is engaged with a flat surface 112 on the shank 102 of the first bucket 104. This allows the radial seal pin 88 to be located closer to the damper pin 74, so that the cooling fluid leakage path 115 in Fig. 7 is reduced relative to the leakage path 100 in Fig. 6 .
  • the damper pin 116 has a uniform, round cross-sectional shape and is relatively loosely seated in a substantially axially-oriented groove 118 in the shank portion 120 of a first bucket 122.
  • the pin 116 is shown in an in-use orientation, engaged with an upper wedge surface 124 of the groove 118 and spaced from the lower surface 126 of the groove due to centrifugal forces.
  • the radial seal pin 128 is relatively loosely seated in a substantially radially-oriented groove 130, also formed on the same side of the shank portion 120 of the bucket 122 as the damper pin groove 118.
  • the damper pin 116 engages a flat surface 132 on the shank portion 134 of the adjacent, second bucket 136, and the radial seal pin 128 is also engaged with the same flat surface 132.
  • the cooling fluid leakage path is shown at 138.
  • Fig. 9 another exemplary but nonlimiting embodiment of the invention is shown where the damper pin 116 and groove 118 in a shank portion 140 of a first bucket 142 are similar to the corresponding groove and pin arrangement in Fig. 7A .
  • the substantially radially-oriented groove 144 is formed in the shank portion 146 of the adjacent or second bucket 148.
  • Damper pin 116 in use, remains engaged with the wedge surface 124 (and spaced from the lower groove surface 126) and a flat surface 150 on the adjacent or second bucket 148, while the radial seal pin 128 is engaged with a flat surface 152 on the first bucket 142.
  • This arrangement also allows the radial seal pin 128 to be located closer to the damper pin 116, so that the leakage path 154 is now smaller than the leakage path 138 in Fig. 8 .
  • each bucket in an annular row of similar buckets has a shank portion with two opposite sides.
  • One side is formed with the substantially axially-oriented damper pin groove, and the opposite side is formed with at least one if not two substantially radially-oriented seal pin grooves (radial seal pins in certain turbine configurations may be installed only on the leading edge of the bucket or blade).
  • radial seal pins in certain turbine configurations may be installed only on the leading edge of the bucket or blade.
  • the adjacent shank portions of any pair of buckets will appear as shown and described in connection with Figs. 4, 5 , 7 and 9 .
  • the invention is not limited to the specifics of the examples described in connection with Figs. 6B and 7B .
  • the invention has wide applicability to various bucket and shank configurations, the constant being the location of damper and radial seal pins on opposite sides of the bucket shank portion.
  • the invention is not limited to specific damper pin and/or seal pin shapes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12158501.2A 2011-03-17 2012-03-07 Dämpfer- und Dichtungsanordnung für eine Turbinenschaufel Active EP2500520B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/050,440 US8905715B2 (en) 2011-03-17 2011-03-17 Damper and seal pin arrangement for a turbine blade

Publications (3)

Publication Number Publication Date
EP2500520A2 true EP2500520A2 (de) 2012-09-19
EP2500520A3 EP2500520A3 (de) 2017-12-27
EP2500520B1 EP2500520B1 (de) 2021-04-28

Family

ID=45833179

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12158501.2A Active EP2500520B1 (de) 2011-03-17 2012-03-07 Dämpfer- und Dichtungsanordnung für eine Turbinenschaufel

Country Status (3)

Country Link
US (1) US8905715B2 (de)
EP (1) EP2500520B1 (de)
CN (1) CN102678191B (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078808A1 (de) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Laufschaufelreihe für eine strömungsmaschine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US11149585B2 (en) 2018-05-24 2021-10-19 MTU Aero Engines AG Turbomachine assembly with a detuning device for different detuning of natural frequencies of the blades
FR3109403A1 (fr) * 2020-04-16 2021-10-22 Safran Aircraft Engines Aube avec organes d’étanchéités améliorés

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JP2015519519A (ja) * 2012-06-15 2015-07-09 ゼネラル・エレクトリック・カンパニイ ロータアセンブリ、対応するガスタービンエンジンおよび組立方法
US10247023B2 (en) 2012-09-28 2019-04-02 United Technologies Corporation Seal damper with improved retention
EP2843197B1 (de) 2013-08-29 2019-09-04 Ansaldo Energia Switzerland AG Schaufel einer rotierenden Strömungsmaschine, wobei die Schaufel eine spezifische Haltevorrichtung für eine radiale Streifendichtung aufweist
US9856737B2 (en) * 2014-03-27 2018-01-02 United Technologies Corporation Blades and blade dampers for gas turbine engines
EP2985419B1 (de) * 2014-08-13 2020-01-08 United Technologies Corporation Turbomaschinenlaufschaufelanordnung mit schaufelfussdichtungen
US9890653B2 (en) * 2015-04-07 2018-02-13 General Electric Company Gas turbine bucket shanks with seal pins
US10316673B2 (en) * 2016-03-24 2019-06-11 General Electric Company CMC turbine blade platform damper
US9845690B1 (en) * 2016-06-03 2017-12-19 General Electric Company System and method for sealing flow path components with front-loaded seal
US10648354B2 (en) 2016-12-02 2020-05-12 Honeywell International Inc. Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing
US10519785B2 (en) * 2017-02-14 2019-12-31 General Electric Company Turbine blades having damper pin slot features and methods of fabricating the same
US11299992B2 (en) * 2020-03-25 2022-04-12 General Electric Company Rotor blade damping structures

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078808A1 (de) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Laufschaufelreihe für eine strömungsmaschine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US11149585B2 (en) 2018-05-24 2021-10-19 MTU Aero Engines AG Turbomachine assembly with a detuning device for different detuning of natural frequencies of the blades
FR3109403A1 (fr) * 2020-04-16 2021-10-22 Safran Aircraft Engines Aube avec organes d’étanchéités améliorés

Also Published As

Publication number Publication date
US20120237352A1 (en) 2012-09-20
US8905715B2 (en) 2014-12-09
EP2500520A3 (de) 2017-12-27
CN102678191A (zh) 2012-09-19
CN102678191B (zh) 2016-01-20
EP2500520B1 (de) 2021-04-28

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